function C = A2I( C,CON )
  %**********************************************************************
  %*** * Propulsion Initialization.
  %*** * Reserved C(3510) locations are 1300-1399
  %*** *
  %*** * * Fixed nozzle, variable fuel flow motor, ideal nozzle expansion
  %*** * is assumed. Throttle ratio THRTL
  %*** * governs the flow rate.
  %*** * * Several stages; the total mass of the remaining stages is initialized
  %*** * by VMASSI; new engine parameters may also be introduced at every
  %*** * stage; the current mass is VMASS;
  %*** *
  %*** * MPROP =0 No ignition; or engine shut-down (D)
  %*** *       =1 Missile is coasting after emgine shut-down.
  %*** *          (shut-down occurs either at fuel burn-out or
  %*** *           when MPROP=0 set in input (G)
  %*** *       =2 Motor ignition; re-ignition; or motor burning (D)
  %*** *
  %*** * This module performs the following functions:
  %*** *
  %*** * (1) Initializes vehicle and fuel masses
  %*** *
  %*** * MODIFICATION HISTORY
  %*** * 000113 Created by Peter Zipfel
  %*** *
  %*** ******************************************************************
  
  %*** INPUT DATA
  
  % EQUIVALENCE (C(1305),VMASSI)
  VMASSI = C(CON.VMASSI);
  
  % VMASSI = D Initial mass of remaining stages - kg
  
  %*** INITIALIZATION

  % EQUIVALENCE (C(1308),FMASSF)
  % EQUIVALENCE (C(1309),VMASS)
  % EQUIVALENCE (C(1312),FMASSFM)
  % EQUIVALENCE (C(1314),VMASSIM)

  % FMASSF = I/G Expended fuel in stage - kg
  % VMASS = I/O Vehicle mass - kg
  % FMASSFM = I Expended fuel in stage, stored - kg
  % VMASSIM = I Initial mass of prior stage - kg

  C(CON.FMASSF) = 0.;
  C(CON.VMASS) = VMASSI;
  C(CON.FMASSFM) = 0.;
  C(CON.VMASSIM) = 0.;

end

